NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA NLF1015 (nlf1015-il) Reynolds number: 500,000 Max Cl/Cd: 130.62 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf1015-il-500000.txt Download as CSV file: xf-nlf1015-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA NLF1015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0143 0.08684 0.08442 -0.1317 0.9402 0.0271
-11.500 -0.0092 0.08119 0.07876 -0.1361 0.9384 0.0273
-11.250 -0.0112 0.07403 0.07161 -0.1399 0.9368 0.0280
-11.000 0.0082 0.07152 0.06907 -0.1424 0.9334 0.0288
-10.750 0.0230 0.06793 0.06545 -0.1458 0.9294 0.0297
-10.500 -0.1098 0.07343 0.07097 -0.1430 0.9392 0.0277
-10.250 -0.0945 0.06953 0.06705 -0.1478 0.9366 0.0283
-10.000 -0.0757 0.06663 0.06413 -0.1522 0.9313 0.0290
-9.750 -0.0578 0.05999 0.05745 -0.1622 0.9266 0.0298
-9.500 -0.0718 0.04603 0.04317 -0.1828 0.9127 0.0299
-9.250 -0.0752 0.04230 0.03924 -0.1869 0.8987 0.0309
-9.000 -0.0871 0.03975 0.03647 -0.1866 0.8854 0.0315
-8.750 -0.0919 0.03711 0.03355 -0.1861 0.8757 0.0327
-8.500 -0.0895 0.03803 0.03399 -0.1839 0.8664 0.0349
-8.250 -0.1018 0.03152 0.02725 -0.1829 0.8588 0.0365
-8.000 -0.0850 0.02994 0.02563 -0.1826 0.8535 0.0374
-7.750 -0.0864 0.02172 0.01607 -0.1789 0.8476 0.0215
-7.500 -0.0674 0.01978 0.01402 -0.1779 0.8430 0.0207
-7.250 -0.0461 0.01812 0.01216 -0.1773 0.8390 0.0203
-7.000 -0.0210 0.01692 0.01076 -0.1773 0.8357 0.0203
-6.750 0.0023 0.01600 0.00972 -0.1769 0.8323 0.0204
-6.500 0.0248 0.01530 0.00894 -0.1762 0.8285 0.0208
-6.250 0.0489 0.01463 0.00819 -0.1759 0.8250 0.0210
-6.000 0.0748 0.01409 0.00756 -0.1759 0.8219 0.0212
-5.750 0.0999 0.01328 0.00667 -0.1761 0.8189 0.0218
-5.500 0.1222 0.01266 0.00604 -0.1756 0.8157 0.0229
-5.250 0.1477 0.01227 0.00563 -0.1757 0.8126 0.0242
-5.000 0.1749 0.01190 0.00520 -0.1760 0.8099 0.0254
-4.750 0.2034 0.01159 0.00481 -0.1766 0.8074 0.0267
-4.500 0.2334 0.01126 0.00442 -0.1775 0.8052 0.0301
-4.250 0.2599 0.01097 0.00416 -0.1776 0.8025 0.0393
-4.000 0.2869 0.01021 0.00385 -0.1785 0.7997 0.1435
-3.750 0.3162 0.00962 0.00365 -0.1798 0.7971 0.2565
-3.500 0.3476 0.00900 0.00346 -0.1816 0.7949 0.3903
-3.250 0.3797 0.00855 0.00343 -0.1833 0.7929 0.5288
-3.000 0.4105 0.00859 0.00353 -0.1841 0.7910 0.5844
-2.750 0.4398 0.00870 0.00364 -0.1846 0.7889 0.6133
-2.500 0.4669 0.00882 0.00376 -0.1845 0.7865 0.6358
-2.250 0.4947 0.00895 0.00387 -0.1846 0.7841 0.6510
-2.000 0.5227 0.00903 0.00395 -0.1847 0.7819 0.6596
-1.750 0.5520 0.00912 0.00400 -0.1851 0.7799 0.6683
-1.500 0.5812 0.00921 0.00407 -0.1855 0.7780 0.6757
-1.250 0.6117 0.00932 0.00410 -0.1863 0.7761 0.6827
-1.000 0.6396 0.00943 0.00423 -0.1864 0.7742 0.6883
-0.750 0.6662 0.00952 0.00432 -0.1864 0.7720 0.6949
-0.500 0.6931 0.00959 0.00440 -0.1864 0.7696 0.7003
-0.250 0.7206 0.00967 0.00450 -0.1864 0.7673 0.7055
0.000 0.7499 0.00975 0.00455 -0.1870 0.7652 0.7112
0.250 0.7792 0.00980 0.00459 -0.1875 0.7632 0.7153
0.500 0.8091 0.00988 0.00467 -0.1881 0.7612 0.7192
0.750 0.8367 0.00999 0.00478 -0.1883 0.7589 0.7236
1.000 0.8628 0.01005 0.00486 -0.1882 0.7560 0.7278
1.250 0.8894 0.01007 0.00492 -0.1881 0.7530 0.7308
1.500 0.9177 0.01009 0.00496 -0.1884 0.7501 0.7336
1.750 0.9480 0.01012 0.00497 -0.1891 0.7473 0.7367
2.000 0.9770 0.01020 0.00505 -0.1896 0.7443 0.7400
2.250 1.0016 0.01024 0.00512 -0.1891 0.7404 0.7432
2.500 1.0282 0.01023 0.00515 -0.1891 0.7366 0.7459
2.750 1.0575 0.01022 0.00516 -0.1895 0.7330 0.7487
3.000 1.0863 0.01028 0.00523 -0.1899 0.7295 0.7516
3.250 1.1093 0.01030 0.00532 -0.1891 0.7251 0.7550
3.500 1.1367 0.01031 0.00534 -0.1892 0.7206 0.7586
3.750 1.1663 0.01030 0.00534 -0.1897 0.7164 0.7615
4.000 1.1882 0.01032 0.00546 -0.1886 0.7112 0.7646
4.250 1.2131 0.01032 0.00550 -0.1882 0.7058 0.7681
4.500 1.2428 0.01034 0.00552 -0.1887 0.7010 0.7718
4.750 1.2624 0.01036 0.00564 -0.1872 0.6947 0.7755
5.000 1.2864 0.01034 0.00567 -0.1865 0.6884 0.7791
5.250 1.3078 0.01037 0.00577 -0.1853 0.6814 0.7833
5.500 1.3294 0.01037 0.00581 -0.1841 0.6729 0.7878
5.750 1.3449 0.01038 0.00589 -0.1815 0.6615 0.7919
6.000 1.3584 0.01040 0.00596 -0.1786 0.6471 0.7964
6.250 1.3658 0.01048 0.00602 -0.1743 0.6277 0.8020
6.500 1.3691 0.01073 0.00621 -0.1693 0.5981 0.8075
6.750 1.3689 0.01124 0.00659 -0.1638 0.5577 0.8138
7.000 1.3665 0.01202 0.00718 -0.1582 0.5170 0.8208
7.250 1.3617 0.01298 0.00798 -0.1523 0.4771 0.8276
7.500 1.3567 0.01413 0.00894 -0.1467 0.4361 0.8356
7.750 1.3520 0.01535 0.01001 -0.1414 0.3965 0.8435
8.000 1.3476 0.01672 0.01121 -0.1365 0.3573 0.8525
8.250 1.3448 0.01813 0.01247 -0.1321 0.3186 0.8628
8.500 1.3424 0.01959 0.01378 -0.1279 0.2818 0.8743
8.750 1.3413 0.02105 0.01512 -0.1240 0.2461 0.8884
9.000 1.3388 0.02257 0.01650 -0.1201 0.2113 0.9078
9.250 1.3332 0.02379 0.01765 -0.1154 0.1811 1.0000
9.500 1.3362 0.02563 0.01926 -0.1131 0.1431 1.0000
9.750 1.3403 0.02740 0.02083 -0.1109 0.1115 1.0000
10.000 1.3428 0.02934 0.02255 -0.1086 0.0781 1.0000
10.250 1.3416 0.03162 0.02458 -0.1061 0.0430 1.0000
10.500 1.3418 0.03389 0.02666 -0.1037 0.0203 1.0000
10.750 1.3500 0.03557 0.02835 -0.1021 0.0158 1.0000
11.000 1.3609 0.03703 0.02987 -0.1009 0.0143 1.0000
11.250 1.3715 0.03853 0.03144 -0.0997 0.0134 1.0000
11.500 1.3809 0.04017 0.03314 -0.0985 0.0126 1.0000
11.750 1.3877 0.04209 0.03512 -0.0971 0.0120 1.0000
12.000 1.3920 0.04429 0.03742 -0.0956 0.0115 1.0000
12.250 1.4011 0.04605 0.03926 -0.0945 0.0112 1.0000
12.500 1.4087 0.04798 0.04129 -0.0934 0.0108 1.0000
12.750 1.4155 0.05005 0.04344 -0.0924 0.0105 1.0000
13.000 1.4210 0.05229 0.04577 -0.0914 0.0102 1.0000
13.250 1.4260 0.05462 0.04819 -0.0904 0.0100 1.0000
13.500 1.4299 0.05713 0.05078 -0.0894 0.0098 1.0000
13.750 1.4336 0.05971 0.05344 -0.0886 0.0096 1.0000
14.000 1.4366 0.06242 0.05624 -0.0878 0.0094 1.0000
14.250 1.4387 0.06529 0.05920 -0.0870 0.0093 1.0000
14.500 1.4406 0.06825 0.06224 -0.0864 0.0091 1.0000
14.750 1.4415 0.07135 0.06545 -0.0858 0.0090 1.0000
15.000 1.4426 0.07451 0.06869 -0.0852 0.0089 1.0000
15.250 1.4440 0.07765 0.07193 -0.0847 0.0088 1.0000
15.500 1.4473 0.08059 0.07497 -0.0840 0.0087 1.0000
15.750 1.4522 0.08335 0.07784 -0.0835 0.0086 1.0000
16.000 1.4566 0.08625 0.08086 -0.0834 0.0085 1.0000
16.250 1.4604 0.08926 0.08400 -0.0834 0.0085 1.0000
16.500 1.4635 0.09239 0.08728 -0.0834 0.0084 1.0000
16.750 1.4657 0.09571 0.09074 -0.0836 0.0084 1.0000
17.000 1.4669 0.09917 0.09435 -0.0838 0.0084 1.0000
17.250 1.4663 0.10296 0.09831 -0.0843 0.0084 1.0000
17.500 1.4645 0.10697 0.10250 -0.0850 0.0083 1.0000
17.750 1.4616 0.11119 0.10690 -0.0859 0.0084 1.0000
18.000 1.4569 0.11576 0.11164 -0.0871 0.0084 1.0000
18.250 1.4498 0.12079 0.11687 -0.0888 0.0084 1.0000
18.500 1.4416 0.12611 0.12237 -0.0909 0.0084 1.0000
18.750 1.4322 0.13175 0.12819 -0.0934 0.0084 1.0000
19.000 1.4216 0.13774 0.13437 -0.0964 0.0084 1.0000
19.250 1.4107 0.14394 0.14075 -0.0998 0.0084 1.0000
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